Patent application number | Description | Published |
20080274336 | High temperature insulation with enhanced abradability - A enhanced abradable friable graded insulator FGI results from the laser patterning of a coating where a series of top surfaces reside on a series of columns such that the walls of the columns are not significantly densified relative to the interior of the columns. Patterns can be generated where the columns are oriented independently normal to or at an acute angle to the top surfaces. The cross sections of the top surfaces are formed to conform to the average dimensions of the spheres of the FGI coating. The cross sections of the top surfaces can be more than 1.5 times the diameter of the spheres. Various patterns of top surfaces can be used including regular, random, quasiperiodic patterns. A gradient of abradability can be imposed on the coating. | 11-06-2008 |
20080279679 | Multivane segment mounting arrangement for a gas turbine - A mounting arrangement ( | 11-13-2008 |
20080280101 | Patterned reduction of surface area for abradability - A gas turbine component ( | 11-13-2008 |
20090010755 | Ceramic matrix composite attachment apparatus and method - An attachment method and flange for connecting a ceramic matrix composite (CMC) component, such as a gas turbine shroud ring ( | 01-08-2009 |
20090071160 | Wavy CMC Wall Hybrid Ceramic Apparatus - A ceramic hybrid structure ( | 03-19-2009 |
20090183850 | Method of Making a Combustion Turbine Component from Metallic Combustion Turbine Subcomponent Greenbodies - A method of making a combustion turbine component includes assembling a plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly and sintering the metallic greenbody assembly to thereby form the combustion turbine component. Each of the plurality of metallic combustion turbine subcomponent greenbodies may be formed by direct metal fabrication (DMF). In addition, each of plurality of metallic combustion turbine subcomponent greenbodies may include an activatable binder and the activatable binder may be activated prior to sintering. | 07-23-2009 |
20090238684 | Cooling arrangement for CMC components with thermally conductive layer - A CMC wall ( | 09-24-2009 |
20090252907 | HYBRID CERAMIC STRUCTURE WITH INTERNAL COOLING ARRANGEMENTS - A structure for use in high temperature applications is provided. The structure may include an inner ceramic matrix composite (CMC) material ( | 10-08-2009 |
20090260364 | Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell - An apparatus for a gas turbine engine, such as a transition ( | 10-22-2009 |
20090324393 | Ceramic matrix composite turbine engine component - Aspects of the invention are directed to a gas turbine component such as a ring seal segment or combustor heat shield having a base and a plurality of walls defining a volume. The base and the walls are independently formed and are formed from ceramic matrix composite plates. The base and walls can have interconnection structures that allow for assembly. The base and walls can be coated or otherwise wrapped for connection. Locking mechanisms, such as self locking lugs, can be used for assembly. | 12-31-2009 |
20100015394 | CERAMIC MATRIX COMPOSITE WALL WITH POST LAMINATE STITCHING - A stitching geometry and method for selective interlaminar reinforcement of a CMC wall ( | 01-21-2010 |
20100047061 | GRID CERAMIC MATRIX COMPOSITE STRUCTURE FOR GAS TURBINE SHROUD RING SEGMENT - A ceramic matrix composite (CMC) component such as a ring seal segment ( | 02-25-2010 |
20100047512 | METHODOLOGY AND TOOLING ARRANGEMENTS FOR STRENGTHENING A SURFACE BOND IN A HYBRID CERAMIC MATRIX COMPOSITE STRUCTURE - A ceramic matrix composite (CMC) structure and methods of fabricating such structure are disclosed. In one example, the surface of a CMC substrate ( | 02-25-2010 |
20100047526 | SUBSURFACE INCLUSIONS OF SPHEROIDS AND METHODOLOGY FOR STRENGTHENING A SURFACE BOND IN A HYBRID CERAMIC MATRIX COMPOSITE STRUCTURE - Structural arrangements and methodology are provided for strengthening a bond between corresponding surfaces of a thermally insulating ceramic coating ( | 02-25-2010 |
20100054930 | TURBINE VANE WITH HIGH TEMPERATURE CAPABLE SKINS - A turbine vane assembly includes an airfoil extending between an inner shroud and an outer shroud. The airfoil can include a substructure having an outer peripheral surface. At least a portion of the outer peripheral surface is covered by an external skin. The external skin can be made of a high temperature capable material, such as oxide dispersion strengthened alloys, intermetallic alloys, ceramic matrix composites or refractory alloys. The external skin can be formed, and the airfoil can be subsequently bi-cast around or onto the skin. The skin and the substructure can be attached by a plurality of attachment members extending between the skin and the substructure. The skin can be spaced from the outer peripheral surface of the substructure such that a cavity is formed therebetween. Coolant can be supplied to the cavity. Skins can also be applied to the gas path faces of the inner and outer shrouds. | 03-04-2010 |
20100074729 | Compressible Ceramic Seal - A stack of substantially parallel ceramic plates ( | 03-25-2010 |
20100075106 | SUBSURFACE INCLUSION OF FUGITIVE OBJECTS AND METHODOLOGY FOR STRENGTHENING A SURFACE BOND IN A HYBRID CERAMIC MATRIX COMPOSITE STRUCTURE - A hybrid ceramic matrix composite (CMC) structure | 03-25-2010 |
20100080953 | Formation of Imprints and Methodology for Strengthening a Surface Bond in a Hybrid Ceramic Matrix Composite Structure - A hybrid ceramic matrix composite structure and method for fabricating such an structure are provided. A ceramic matrix composite substrate | 04-01-2010 |
20100119777 | Ceramic matrix composite surfaces with open features for improved bonding to coatings - A method to form an improved hybrid ceramic matrix composite structure comprises providing a ceramic matrix composite (CMC) with open features at a surface and applying a thermal barrier coating to the surface. The thermal barrier coating is preferably a friable graded insulation coating (FGI) having hollow ceramic spheres. For acceptance of a FGI coating the open features have a center-to-center separation distance in one or more directions that is between about 100 and about 1,000 percent of the diameter of the hollow ceramic spheres in the FGI and a depth that is between about 20 percent and about 200 percent of the diameter of the hollow ceramic spheres in the FGI. The open feature can result from the winding of tows about a mandrel; the lay-up of fabric including a surface fabric having an open weave; or the use of a 3-D weave, or a 3-D braid. | 05-13-2010 |
20100119807 | CMC WITH MULTIPLE MATRIX PHASES SEPARATED BY DIFFUSION BARRIER - A ceramic matrix composite (CMC) material ( | 05-13-2010 |
20100150703 | STACKED LAMINATE BOLTED RING SEGMENT - A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a bolt or a plurality of bolts designed to prevent delamination of the ceramic plates when in use by keeping the ceramic plates in compression. | 06-17-2010 |
20100183435 | Gas Turbine Vane Platform Element - A gas turbine CMC shroud plate ( | 07-22-2010 |
20100221485 | THREE DIMENSIONAL REINFORCED CMC ARTICLES BY INTERLOCKING TWO DIMENSIONAL STRUCTURES - The interlocking of two or more sections via the insertion of one or more out-of-plane features in one section or combination of sections through a void in one or more a complementary sections can result in a reinforced ceramic matrix composite article upon securing of the sections. The sections can be secured by friction between two tightly matched sections or by the use of a pin, hook, or clamp. The sections can be constructed from one or more CMC laminate sheets. The out-of-plane feature can be a loop or a flange and the void can be an orifice or a matched loop in the complementary sheet. The securing of the sections can result in a CMC article where the delamination between sheets is inhibited. | 09-02-2010 |
20100251721 | Stacked laminate gas turbine component - A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material. | 10-07-2010 |
20100263194 | ATTACHMENT FOR CERAMIC MATRIX COMPOSITE COMPONENT - A bushing ( | 10-21-2010 |
20100279072 | Gussets for Strengthening CMC Fillet Radii - A ceramic matrix composite (CMC) structure ( | 11-04-2010 |
20100284798 | Turbine Airfoil With Dual Wall Formed from Inner and Outer Layers Separated by a Compliant Structure - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a compliant structure. The compliant structure may be configured such that the outer layer may thermally expand without limitation by the inner layer. The compliant structure may be formed from a plurality of pedestals positioned generally parallel with each other. The pedestals may include a first foot attached to a first end of the pedestal and extending in a first direction aligned with the outer layer, and may include a second foot attached to a second end of the pedestal and extending in a second direction aligned with the inner layer. | 11-11-2010 |
20100284822 | Turbine Airfoil with a Compliant Outer Wall - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation in the outer layer is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a support structure. The outer layer may be a compliant layer configured such that the outer layer may thermally expand and thereby reduce the stress within the outer layer. The outer layer may be formed from a nonplanar surface configured to thermally expand. In another embodiment, the outer layer may be planar and include a plurality of slots enabling unrestricted thermal expansion in a direction aligned with the outer layer. | 11-11-2010 |
20100291348 | Methodology and Tooling Arrangements for Increasing Interlaminar Shear Strength in a Ceramic Matrix Composite Structure - Methodology and tooling arrangements for increasing interlaminar shear strength in a ceramic matrix composite (CMC) structure are provided. The CMC structure may be formed by a plurality of layers of ceramic fibers disposed between a top surface and a bottom surface of the composite structure. A plurality of surface recesses are formed on the surfaces of the structure. For example, each of the surfaces of the composite structure may be urged against corresponding top and bottom surfaces of a tool having a plurality of asperities. The plurality of surface recesses causes an out-of-plane sub-surface fiber displacement along an entire thickness of the structure, and the sub-surface fiber displacement is arranged to increase an interlaminar shear strength of the structure. | 11-18-2010 |
20100291349 | Subsurface Inclusions of Objects for Increasing Interlaminar Shear Strength of a Ceramic Matrix Composite Structure - A ceramic matrix composite (CMC) structure | 11-18-2010 |
20100322760 | Interlocked CMC Airfoil - A ceramic matrix composite (CMC) airfoil assembled from a pressure side wall ( | 12-23-2010 |
20100322774 | Airfoil Having an Improved Trailing Edge - An airfoil ( | 12-23-2010 |
20110041313 | Joining Mechanism with Stem Tension and Interlocked Compression Ring | 02-24-2011 |
20110142684 | Turbine Engine Airfoil and Platform Assembly - A turbine airfoil ( | 06-16-2011 |
20110243724 | TURBINE AIRFOIL TO SHROUND ATTACHMENT - A turbine airfoil ( | 10-06-2011 |
20110265406 | GUSSET WITH FIBERS ORIENTED TO STRENGTHEN A CMC WALL INTERSECTION ANISOTROPICALLY | 11-03-2011 |
20120000072 | Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components - A method of making a combustion turbine component includes forming a metallic body by direct metal fabrication (DMF) to have at least one surface portion defining a first plurality of surface cooling features each having a first dimension and at least one second surface cooling feature on at least one of the first plurality of surface cooling features and having a second dimension less than said first dimension and less than 200 μm. Forming the metallic body by DMF may include forming a plurality of metallic combustion turbine subcomponent greenbodies by DMF and assembling the plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly. The metallic greenbody assembly may be sintered to thereby form the metallic body. | 01-05-2012 |
20120006518 | MESH COOLED CONDUIT FOR CONVEYING COMBUSTION GASES - A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having an inner surface, an outer surface, a region, an inlet, and an outlet. The inner surface defines an inner volume of the conduit. The region extends between the inner and outer surfaces and includes cooling fluid structure defining a plurality of cooling passageways. The inlet extends inwardly from the outer surface and provides fluid communication between the inlet and the passageways. The outlet extends from the passageways to the inner surface to provide fluid communication between the passageways and the inner volume. At least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through the first cooling passageway interacts with cooling fluid flowing through the second cooling passageway. | 01-12-2012 |
20120125585 | CMC WALL STRUCTURE WITH INTEGRAL COOLING CHANNELS - A ceramic matrix composite wall structure ( | 05-24-2012 |
20120148794 | CMC ANCHOR FOR ATTACHING A CERAMIC THERMAL BARRIER TO METAL - A ceramic matrix composite (CMC) anchor ( | 06-14-2012 |
20120295067 | Methodology and tooling arrangements for increasing interlaminar shear strength in a ceramic matrix composite structure - Methodology and tooling arrangements for increasing interlaminar shear strength in a ceramic matrix composite (CMC) structure are provided. The CMC structure may be formed by a plurality of layers of ceramic fibers disposed between a top surface and a bottom surface of the composite structure. A plurality of surface recesses are formed on the surfaces of the structure. For example, each of the surfaces of the composite structure may be urged against corresponding top and bottom surfaces of a tool having a plurality of asperities. The plurality of surface recesses causes an out-of-plane sub-surface fiber displacement along an entire thickness of the structure, and the sub-surface fiber displacement is arranged to increase an interlaminar shear strength of the structure. | 11-22-2012 |
20140294652 | Method of Making a Combustion Turbine Component from Metallic Combustion Turbine Subcomponent Greenbodies - A method of making a combustion turbine component includes assembling a plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly and sintering the metallic greenbody assembly to thereby form the combustion turbine component. Each of the plurality of metallic combustion turbine subcomponent greenbodies may be formed by direct metal fabrication (DMF). In addition, each of plurality of metallic combustion turbine subcomponent greenbodies may include an activatable binder and the activatable binder may be activated prior to sintering. | 10-02-2014 |